JPS6347881B2 - - Google Patents
Info
- Publication number
- JPS6347881B2 JPS6347881B2 JP57117723A JP11772382A JPS6347881B2 JP S6347881 B2 JPS6347881 B2 JP S6347881B2 JP 57117723 A JP57117723 A JP 57117723A JP 11772382 A JP11772382 A JP 11772382A JP S6347881 B2 JPS6347881 B2 JP S6347881B2
- Authority
- JP
- Japan
- Prior art keywords
- turbine shroud
- turbine
- heat insulating
- rotor
- cast iron
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired
Links
- 239000000919 ceramic Substances 0.000 claims description 21
- 229910052751 metal Inorganic materials 0.000 claims description 6
- 239000002184 metal Substances 0.000 claims description 6
- 229910001018 Cast iron Inorganic materials 0.000 description 12
- 238000004519 manufacturing process Methods 0.000 description 3
- 239000000463 material Substances 0.000 description 3
- VYPSYNLAJGMNEJ-UHFFFAOYSA-N Silicium dioxide Chemical compound O=[Si]=O VYPSYNLAJGMNEJ-UHFFFAOYSA-N 0.000 description 2
- 229910052782 aluminium Inorganic materials 0.000 description 2
- 238000005266 casting Methods 0.000 description 2
- 239000002657 fibrous material Substances 0.000 description 2
- 239000011810 insulating material Substances 0.000 description 2
- 239000012212 insulator Substances 0.000 description 2
- 229910052710 silicon Inorganic materials 0.000 description 2
- PIGFYZPCRLYGLF-UHFFFAOYSA-N Aluminum nitride Chemical compound [Al]#N PIGFYZPCRLYGLF-UHFFFAOYSA-N 0.000 description 1
- 229910001141 Ductile iron Inorganic materials 0.000 description 1
- 229910001060 Gray iron Inorganic materials 0.000 description 1
- 229910052581 Si3N4 Inorganic materials 0.000 description 1
- XUIMIQQOPSSXEZ-UHFFFAOYSA-N Silicon Chemical compound [Si] XUIMIQQOPSSXEZ-UHFFFAOYSA-N 0.000 description 1
- 230000002745 absorbent Effects 0.000 description 1
- 239000002250 absorbent Substances 0.000 description 1
- 239000006096 absorbing agent Substances 0.000 description 1
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 1
- PNEYBMLMFCGWSK-UHFFFAOYSA-N aluminium oxide Inorganic materials [O-2].[O-2].[O-2].[Al+3].[Al+3] PNEYBMLMFCGWSK-UHFFFAOYSA-N 0.000 description 1
- 230000003139 buffering effect Effects 0.000 description 1
- 150000001875 compounds Chemical class 0.000 description 1
- 238000005336 cracking Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000001066 destructive effect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000009413 insulation Methods 0.000 description 1
- 239000003562 lightweight material Substances 0.000 description 1
- 239000007788 liquid Substances 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 229910052757 nitrogen Inorganic materials 0.000 description 1
- 239000003921 oil Substances 0.000 description 1
- 229910052760 oxygen Inorganic materials 0.000 description 1
- 230000002093 peripheral effect Effects 0.000 description 1
- 239000011505 plaster Substances 0.000 description 1
- 239000000843 powder Substances 0.000 description 1
- 238000007789 sealing Methods 0.000 description 1
- 230000035939 shock Effects 0.000 description 1
- 239000010703 silicon Substances 0.000 description 1
- HBMJWWWQQXIZIP-UHFFFAOYSA-N silicon carbide Chemical compound [Si+]#[C-] HBMJWWWQQXIZIP-UHFFFAOYSA-N 0.000 description 1
- 239000000377 silicon dioxide Substances 0.000 description 1
- HQVNEWCFYHHQES-UHFFFAOYSA-N silicon nitride Chemical compound N12[Si]34N5[Si]62N3[Si]51N64 HQVNEWCFYHHQES-UHFFFAOYSA-N 0.000 description 1
- 238000007582 slurry-cast process Methods 0.000 description 1
- 239000000725 suspension Substances 0.000 description 1
- 230000008646 thermal stress Effects 0.000 description 1
- 230000001052 transient effect Effects 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/026—Scrolls for radial machines or engines
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/08—Cooling; Heating; Heat-insulation
- F01D25/14—Casings modified therefor
- F01D25/145—Thermally insulated casings
Description
【発明の詳細な説明】
本発明は、タービンシユラウド、とくにターボ
チヤージヤ等のタービンシユラウドに関する。DETAILED DESCRIPTION OF THE INVENTION The present invention relates to a turbine shroud, particularly a turbine shroud such as a turbocharger.
従来のタービンシユラウドとしては、例えば第
１図に示すようなものがある（特公昭50−35604
号参照のこと）。ここで、１は図示しないコンプ
レツサーとロータ軸２を介して直結されているタ
ービンロータであり、ロータ軸２はフローテイン
グメタル３に軸支されたセンターハウジング４に
収納されている。タービンロータ１の外周部には
排気ガスをロータ１に導くスクロール５とこれに
連なるロータチツプシユラウド６とが一体のター
ビンシユラウド７として鋳物で形成されており、
スクロール５から導入されたガスはロータ１を回
転させて排出口から排出される。８はオイル漏れ
を防止しているシールリングである。 For example, there is a conventional turbine shroud as shown in Figure 1 (Special Publication No. 50-35604
(see issue). Here, 1 is a turbine rotor that is directly connected to a compressor (not shown) via a rotor shaft 2, and the rotor shaft 2 is housed in a center housing 4 that is pivotally supported by a floating metal 3. On the outer periphery of the turbine rotor 1, a scroll 5 for guiding exhaust gas to the rotor 1 and a rotor tip shroud 6 connected thereto are formed by casting as an integrated turbine shroud 7.
The gas introduced from the scroll 5 rotates the rotor 1 and is discharged from the exhaust port. 8 is a seal ring that prevents oil leakage.
タービンシユラウド７を形成する鋳物としては
ダクタイル鋳鉄、ハイシリコン鋳鉄など熱的に強
い鋳鉄が用いられており、タービンシユラウド７
はリテーナ９を介して植込ボルト１０とナツト１
１によりセンタハウジング４に取付けられてい
る。 As the casting that forms the turbine shroud 7, thermally strong cast iron such as ductile cast iron and high silicon cast iron is used.
is the stud bolt 10 and nut 1 via the retainer 9.
1 is attached to the center housing 4.
なお、タービンシユラウド７とセンタハウジン
グ４との間にはインシユレータ１２が介装されて
いて、排気ガスによつて加熱されたタービンシユ
ラウド７の熱がセンタハウジング４に伝わるのを
防止する。 An insulator 12 is interposed between the turbine shroud 7 and the center housing 4 to prevent heat from the turbine shroud 7 heated by exhaust gas from being transmitted to the center housing 4.
しかしながら、このような従来のタービンシユ
ラウドにあつては、鋳鉄でタービンシユラウド７
全体が形成されているので、つぎのような問題点
があつた。 However, in such conventional turbine shrouds, the turbine shroud 7 is made of cast iron.
Since the entire structure was formed, the following problems arose.
(1) タービンシユラウド７の内面が高温の排気ガ
スと接触していることにより、浸食を受けて破
損したり、あるいは、破損しなくても荒れを生
じタービン効率が低下する。(1) Since the inner surface of the turbine shroud 7 is in contact with high-temperature exhaust gas, it may be eroded and damaged, or even if it is not damaged, it may become rough and reduce turbine efficiency.
(2) 高温の排気ガスに耐えるよう、高価な耐熱性
のある鋳鉄を用いるので生産コストが高い。(2) Production costs are high because expensive heat-resistant cast iron is used to withstand high-temperature exhaust gas.
(3) タービンロータ１が金属製の場合は、ロータ
１の破損によつて生じる万一のバーストに備え
る必要からタービンシユラウド７の肉厚を厚く
とるので重量が重くなる。(3) When the turbine rotor 1 is made of metal, the thickness of the turbine shroud 7 is increased because it is necessary to prepare for an unexpected burst caused by damage to the rotor 1, which increases the weight.
(4) 鋳鉄は伝熱性が良いので排気ガスの熱が外部
に伝えられ、エンジンルームの温度が上る。(4) Cast iron has good heat conductivity, so the heat of exhaust gas is transferred to the outside, raising the temperature of the engine compartment.
そこで、本発明の目的は、これらの問題を解消
し、排気ガスに浸食されるようなことがなく、重
量が軽くて、しかも廉価で得られるタービンシユ
ラウドを提供することにある。 SUMMARY OF THE INVENTION An object of the present invention is to solve these problems and provide a turbine shroud that is not eroded by exhaust gas, is light in weight, and can be obtained at low cost.
かかる目的を達成するために、本発明は、高温
ガスに接するロータチツプシユラウドとスクロー
ルとが一体に構成されるタービンシユラウドにお
いて、ロータチツプシユラウドとスクロールとの
高温ガスに接する面を薄肉のセラミツクス層で構
成し、セラミツクス層の外側全周を断熱層によつ
て被覆し、当該断熱層の外側に鋳ぐるみによる金
属製ケーシングを設けたことを特徴とするのであ
る。 In order to achieve such an object, the present invention provides a turbine shroud in which a rotor tip loud and a scroll that are in contact with high-temperature gas are integrally formed, and the surfaces of the rotor tip loud and scroll that are in contact with high-temperature gas are thin-walled. It is characterized in that it is composed of a ceramic layer, the entire outer circumference of the ceramic layer is covered with a heat insulating layer, and a metal casing made of cast iron is provided outside the heat insulating layer.
以下、図面を参照して本発明を詳細に説明す
る。 Hereinafter, the present invention will be explained in detail with reference to the drawings.
第２図は本発明の一実施例を示す。ここで、１
７はタービンシユラウドであり、そのスクロール
５からロータチツプシユラウド６にいたる内周面
の層１８をセラミツクスで形成する。セラミツク
ス層１８の形成には、吸収性のある石膏型に、窒
化硅素（Si3N4）、炭化硅素（SiC）、窒化アルミ
ニウム（AlN）、サイアロン（Si、Al、Ｏ、Ｎよ
りなる化合物）などの粉末を液体に懸濁させたも
のを流し込み乾燥させる泥漿鋳込み法等によるこ
とが考えられる。 FIG. 2 shows an embodiment of the invention. Here, 1
Reference numeral 7 denotes a turbine shroud, and a layer 18 on the inner circumferential surface from the scroll 5 to the rotor tip shroud 6 is formed of ceramics. To form the ceramic layer 18, silicon nitride (Si 3 N 4 ), silicon carbide (SiC), aluminum nitride (AlN), and Sialon (a compound consisting of Si, Al, O, and N) are added to an absorbent plaster mold. Possible methods include slurry casting, in which a suspension of powder, such as, in a liquid is poured and dried.
しかして、その周囲にアルミナ、シリカなどか
らなる多孔質断熱材やセラミツクス繊維材の断熱
層１９をめぐらし、このように形成したセラミツ
クス層１８および断熱層１９をねずみ鋳鉄などの
廉価な鋳鉄により鋳ぐるみして、一本化したター
ビンシユラウド１７を構成する。なお、ここで、
セラミツクス層１８は過大な過渡的熱応力を避け
るために薄肉とするのが好適である。その他の構
造は従来例と全く同じである。 Then, a heat insulating layer 19 made of a porous heat insulating material made of alumina, silica, etc. or a ceramic fiber material is placed around it, and the ceramic layer 18 and heat insulating layer 19 thus formed are cast with inexpensive cast iron such as gray cast iron. Thus, an integrated turbine shroud 17 is constructed. Furthermore, here,
Ceramic layer 18 is preferably thin to avoid excessive transient thermal stresses. The other structure is exactly the same as the conventional example.
このように構成したタービンシユラウドでは、
シユラウド１７の内周面をセラミツクス層１８で
形成したので、排気ガスの温度が高い場合でも浸
食されたり破損することがない。 In the turbine shroud configured in this way,
Since the inner peripheral surface of the shroud 17 is formed of the ceramic layer 18, it will not be eroded or damaged even when the exhaust gas temperature is high.
更にセラミツクス層１８の周囲に設けた多孔質
断熱材やセラミツクス繊維材の断熱層１９は外部
への伝熱を抑制すると共に多少の変形を許し緩衝
材としての役割を果すので、鋳鉄ケーシング２０
でセラミツクス層１８および断熱層１９を鋳ぐる
んでも、そのときのケーシングの収縮によつてセ
ラミツクス層１８が破壊されるのを防止すること
ができる。 Furthermore, the porous heat insulating material or the heat insulating layer 19 made of ceramic fiber material provided around the ceramic layer 18 suppresses heat transfer to the outside, allows some deformation, and serves as a buffer material, so that the cast iron casing 20
Even if the ceramic layer 18 and the heat insulating layer 19 are cast inside, it is possible to prevent the ceramic layer 18 from being destroyed by the shrinkage of the casing at that time.
更にまた、鋳鉄ケーシング２０用材料は耐熱性
を要求されないので、廉価な鋳鉄を用いることが
できる。 Furthermore, since the material for the cast iron casing 20 is not required to be heat resistant, inexpensive cast iron can be used.
なお、タービンロータ１にもセラミツクを適用
した場合には、バースト時の破壊力が小さく、同
時に断熱層１９も衝撃吸収材として働くので、ケ
ーシング２０を従来に比べて薄肉化でき、あるい
はアルミニウム材などの軽量材の適用が可能であ
る。 Note that if ceramic is also used for the turbine rotor 1, the destructive force at the time of burst is small, and at the same time the heat insulating layer 19 also acts as a shock absorber, so the casing 20 can be made thinner than conventional ones, or it can be made of aluminum or other materials. It is possible to apply lightweight materials.
さらに、タービンシユラウド１７全体をセラミ
ツクスにて製作することが考えられるが、このよ
うにすると肉厚になつて製作が困難であるのみな
らず、熱膨張の異なるセンタハウジング４への装
着が困難であるなどの欠陥がある。 Furthermore, it is conceivable to manufacture the entire turbine shroud 17 from ceramics, but this would not only make it thick and difficult to manufacture, but also make it difficult to attach it to the center housing 4, which has a different thermal expansion. There are some defects.
また、本発明では断熱層を介してセラミツク層
を鋳鉄で鋳くるんだ構成としたので、ある程度の
衝撃には耐えられ、整備時に工具をタービンシユ
ラウド１７に落とすようなことがあつても、この
ためにセラミツクスが割れるような心配がない。 In addition, since the present invention has a structure in which the ceramic layer is encased in cast iron with a heat insulating layer in between, it can withstand a certain degree of impact, and even if a tool is dropped into the turbine shroud 17 during maintenance, it will not be damaged. There is no need to worry about the ceramics cracking.
以上から明らかなように、本発明によれば、タ
ービンシユラウドを耐熱性のあるセラミツクス薄
肉層の周囲に緩衝効果を有する断熱層をめぐら
し、これらを廉価な鋳鉄などで鋳ぐるんだ構造と
したので、タービンシユラウドの耐熱性が向上
し、破損やタービン効率の低下をきたさず、装置
コストを低減でき、タービンシユラウドの重量を
軽減でき、しかもまた、外部への伝熱を抑制する
ことができるなどの効果が得られる。 As is clear from the above, according to the present invention, the turbine shroud has a structure in which a heat-resistant ceramic thin layer is surrounded by a heat-insulating layer having a buffering effect, and these are cast with inexpensive cast iron or the like. This improves the heat resistance of the turbine shroud, prevents damage and reduces turbine efficiency, reduces equipment costs, reduces the weight of the turbine shroud, and also suppresses heat transfer to the outside. You can get effects such as:
第１図は従来のターボチヤージヤにおけるガス
タービンシユラウド近傍構造を示す断面図、第２
図は本発明ターボチヤージヤにおけるガスタービ
ンシユラウド近傍の構造の一例を示す断面図であ
る。
１……タービンロータ、２……ロータ軸、３…
…フローテングメタル、４……センターハウジン
グ、５……スクロール、６……ロータチツプシユ
ラウド、７……タービンシユラウド、８……シー
リング、９……リラーナ、１０……植込ボルト、
１１……ナツト、１２……インシユレータ、１７
……タービンシユラウド、１８……セラミツクス
層、１９……断熱層、２０……ケーシング。
Figure 1 is a sectional view showing the structure near the gas turbine shroud in a conventional turbocharger;
The figure is a sectional view showing an example of the structure near the gas turbine shroud in the turbocharger of the present invention. 1... Turbine rotor, 2... Rotor shaft, 3...
... Floating metal, 4 ... Center housing, 5 ... Scroll, 6 ... Rotor tip shroud, 7 ... Turbine shroud, 8 ... Sealing, 9 ... Relana, 10 ... Studded bolt,
11...Natsuto, 12...Insulator, 17
... Turbine shroud, 18 ... Ceramics layer, 19 ... Heat insulation layer, 20 ... Casing.
Claims (1)
スクロールとが一体に構成されるタービンシユラ
ウドにおいて、前記ロータチツプシユラウドとス
クロールとの前記高温ガスに接する面を薄肉のセ
ラミツクス層で構成し、該セラミツクス層の外側
全周を断熱層によつて被覆し、当該断熱層の外側
に鋳ぐるみによる金属製ケーシングを設けたこと
を特徴とするタービンシユラウド。1. In a turbine shroud in which a rotor tip loud and a scroll that are in contact with high-temperature gas are integrally formed, the surfaces of the rotor tip loud and scroll that are in contact with the high-temperature gas are made of a thin ceramic layer, and the ceramic layer is made of a thin ceramic layer. A turbine shroud, characterized in that the entire outer circumference of the turbine shroud is covered with a heat insulating layer, and a metal casing made of cast metal is provided outside the heat insulating layer.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP11772382A JPS5910709A (en) | 1982-07-08 | 1982-07-08 | Turbine shroud |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP11772382A JPS5910709A (en) | 1982-07-08 | 1982-07-08 | Turbine shroud |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| JPS5910709A JPS5910709A (en) | 1984-01-20 |
| JPS6347881B2 true JPS6347881B2 (en) | 1988-09-26 |
Family
ID=14718687
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP11772382A Granted JPS5910709A (en) | 1982-07-08 | 1982-07-08 | Turbine shroud |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPS5910709A (en) |
Families Citing this family (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS6024839U (en) * | 1983-07-27 | 1985-02-20 | いすゞ自動車株式会社 | Turbocharger insulation structure |
| JPH0629523B2 (en) * | 1985-04-23 | 1994-04-20 | 日産自動車株式会社 | Turbine housing |
| JPS6296734A (en) * | 1985-10-22 | 1987-05-06 | Isuzu Motors Ltd | Turbosupercharger |
| JPH0619808Y2 (en) * | 1988-06-07 | 1994-05-25 | 日産自動車株式会社 | Turbocharger |
| US4978278A (en) * | 1989-07-12 | 1990-12-18 | Union Carbide Corporation | Turbomachine with seal fluid recovery channel |
| DE10310678B3 (en) * | 2003-03-12 | 2004-09-23 | Atlas Copco Energas Gmbh | Expansion turbine stage |
| WO2005108747A1 (en) * | 2004-05-12 | 2005-11-17 | Honeywell International Inc. | Turbocharger with reduced thermal inertia and method of producing the same |
| US8984895B2 (en) * | 2010-07-09 | 2015-03-24 | Icr Turbine Engine Corporation | Metallic ceramic spool for a gas turbine engine |
| DE102011003424A1 (en) * | 2011-02-01 | 2012-08-02 | Continental Automotive Gmbh | Turbine of an exhaust gas turbocharger and turbocharger with such a turbine for a motor vehicle |
| CN103429869B (en) * | 2011-04-26 | 2015-06-10 | 丰田自动车株式会社 | Turbine housing for turbocharger |
| US10094288B2 (en) | 2012-07-24 | 2018-10-09 | Icr Turbine Engine Corporation | Ceramic-to-metal turbine volute attachment for a gas turbine engine |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS4861808A (en) * | 1971-11-18 | 1973-08-29 | ||
| JPS5776230A (en) * | 1980-10-22 | 1982-05-13 | Gen Motors Corp | Gas turbine engine |
-
1982
- 1982-07-08 JP JP11772382A patent/JPS5910709A/en active Granted
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS4861808A (en) * | 1971-11-18 | 1973-08-29 | ||
| JPS5776230A (en) * | 1980-10-22 | 1982-05-13 | Gen Motors Corp | Gas turbine engine |
Also Published As
| Publication number | Publication date |
|---|---|
| JPS5910709A (en) | 1984-01-20 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US4495684A (en) | Process of joining a ceramic insert which is adapted to be embedded in a light metal casting for use in internal combustion engines | |
| US4245611A (en) | Ceramic insulated engine pistons | |
| JPS6347881B2 (en) | ||
| JPS5842149B2 (en) | A combination between a ceramic part and a metal part | |
| JPS60101201A (en) | Joining structure in turbine shaft | |
| US5404721A (en) | Cast-in-place ceramic manifold and method of manufacturing same | |
| JPH07259642A (en) | Heat-insulating port liner assembly | |
| US4524732A (en) | Cylinder head of a piston engine | |
| JPS6350195B2 (en) | ||
| JPH0375744B2 (en) | ||
| US3664766A (en) | Turbine wheel | |
| JPH02104950A (en) | Piston for internal combustion engine | |
| JP2699586B2 (en) | Adiabatic piston and method of manufacturing the same | |
| US4516480A (en) | Piston ring for endothermic motors having an improved flame damper ring | |
| JPH0322533Y2 (en) | ||
| JPS6220666Y2 (en) | ||
| JPS6044506B2 (en) | Internal combustion engine cylinder liner | |
| JPS5819325Y2 (en) | Internal combustion engine piston head member | |
| JPS6313384Y2 (en) | ||
| JPH03124944A (en) | Heat insulating engine component, manufacture thereof and heat insulating piston | |
| JPS595809A (en) | Turbine housing | |
| JPH05256191A (en) | Exhaust passage for combustion equipment | |
| JPH037561Y2 (en) | ||
| JPS6114596Y2 (en) | ||
| JPH05256104A (en) | Turbine housing |